Safety tank and fuel system for aircraft



June 9, 1942. w. w. PAGET 2,235,830

. SAFETY TANK AND FUEL SYSTEM FOR AIRCRAFT Fi1 ed Jan. 13. 1959 2 a Patented June 9, 1942 REIS SUED v Auc21194l uu reo .sf A'rss PATENT OFFICE ssm'rr rm rum. srsrsu Iron 'William Willard Faget, Newark, N. J. Application January-1S, 19:9, Serial No. 250,846

BClaims.

The invention relates to improvements in tanks and fuel systemsfor aircraft: the objects I of the improvement are principally toprovide a really safe fuel-supply and fuel system and one'with the particularly great hazards of .fire heretofore present, and previously not elsewhere fully now clearly apprehended hereby, and now by this improvement most effectually remedied closed and described.

- Heretofore in the midst of fire and flame the. fuel tank or tanks rapidly become pressure kettles spurting and spouting blazing fuel under pressure from every opening in fuel line actually feeding the flames in progressive stages and increasing fury"and intensity to its own ultimate end and destruction. 4 Broken fuel lines in crashes presented further complications and added to the interrelated phenomena of this firev and explosion hazard problem; a broken fuel line meaning usually direct free and ready access and ingress of'flames and fire through the broken fuel line to the interior of tank and contents with resultant explosion attendant thereupon. This being a part of-the original discovery 'by the present applicant and inventor: and further great "spillage I .of fuel' likewise followed these breaks in fuel lines. The anti-explosion devices or flame-arresters I. are therefore provided in the fuel lines interdependently and cooperatively working in conjunction and combination with the heat and flame impermeable insulating jacket '3, and the automatic self-closing valves 1 and 9 also provided in close interrelated turn. An automatic self-closing valve cannot dependably be counted upon to operate quickly enoughto prevent the flashback through said valve .before it is fully closed for the anti-explosion device or flamearresters are provided to efficiently and effectual- 1y cooperate with and support said self-closingv valves 1 and 9 in combination therewith to effeet and accomplish emciently the long sought desideratum and purpose. But the. flame-ar'-' resters l, of. themselves alone will not operateeti and current source respectively 'as' used in a- (cuss-48).

dependably or successfully over long periods of time and, therefore, it in turn requires the automatic self-closing valve herewith provided by the present applicant and inventor to'operate in'coniunction and in combination with same and both require and need the heat and flame impermeable insulating Jacket 3 to-themselves operate dependably at all or over long periods of time as described.

10 All of which demanded the euually cooperative structure and interrelated combination of elements devolved. developed. and discovered by the present applicant and inventor as herewith set forth and described.

system layout is here illustrated in the accompanying drawing.

And while the form .vention is here shown comprised in a typical or specimen fuel system layout it will be readily seen and understood that there are a number of modifications hereof all properly within the aim, scope, field, and purport of this invention,

and so as such by-me here reserved and claimed.

"Io witthe improvement (is highly adapted H to the so called "self-sealing type and other tanks over which it may be truly looked upon as a markedly advanced improvement.

80 In the drawing Figure 1 is a -side elevation view of a fuel tank in part sectioned and showing some of the connections of thefuel line.

'vided the safety tank and-fuel system embodied as in Figs. 1 and 2. Figure 3 is a diagrammatic ment.

With reference to the drawing in Figure l, the

'io fiumeral l indicates a fuel tank, 2 is the fuel line,

3 is the all important heat and flame 'impermeable insulating Jacket which may comprise mineral wool, asbestos, magnesia or aluminum foil, .and l are the anti-explosion devices. or r f flame arresters, so called effectually interdependably, and successively progressively operating cooperatlvely in turn with 3, and I which is an automatic self-closing. shut-oi! valve, preferably of the differential spring loaded or other equally I suitabletype. "is a non-return or back-pressure or self closing check valve as provided in said fuel inlet; '8 is a fuel pump. In Fig. 3 0 is another type of automatic or self-closingvalve: ll and II are an optional electric control circuit One form and embodiment of the invention as typically shown in anoptional specimen fuel- I or embodiment of the in-. v

Figure 2 illustrates an aircraft in which is proview in part sectioned of a complete typical fuel system for aircraft provided. with the improve-' a nonreturn valve it as shpw'nin Fig. 1; I1 is a strainer; 22 is a carburetor in an aircraft?" is manifold; 24. is an engine, and l is a typical fuel pump. Fig. 2 illustrates anaircraft in which is installed a fuel tank of the type shown in Figs.

land3; Y

And while! have here shown the form or embodiment of the improvement provided in a con- BQBILSSO modification; l2 is a part of saldelectric control circuit; and It is a switch as employed in said modified system; II -is ai'illing pipe provided with ventional or typical "fuel system piping layout a with one or more fuel tanks and essential parts, it

will be readily understood and apprehended that the herewith described safety system is readily adapted to any method of fuel piping or other ta types or modifications thereof, and all properly well within the aim, scope, field, object, and fulhpurport of the invention and so me reserved and claimed.

I claim:

as such by v 1. In a safety fuel system for aircraft comand flame impermeable insulation jacket itself I being of material incombustible and toheat or flre.'

. 3. A safety tank for aircraft comprisi l a fuel container provided with a high-temperature heat andflame impermeable insulating jacket coniposed preferablyof a suitable mineral substance or material such as mineral wool, asbestos, or

- the like or the equivalent thereto as means for inhibiting or preventing the ingress of heat or flame to the interior and fuel contents of said tank in event of flre.

4; Asafety tank and fuel system foraircraft,

said safety tank and fuel lines comprising or being provided with an especial heat and flame impermeable jacket specially adapted to effectively prevent the transfer or on of heat to the interior of tank and contents during the period and progress of external flame or me and said heat and flame impermeable insulating jacket being essentially incombustible, non-inflammable, and immune to heat and flre.

5. In an airplane or the like, a fuel tank-of so- I called military self-sealing? or other typ and said'military or other type of tank being suitably provided with a heat and flame impermeable 2. A safetyifuel tank of so-called self-sealing military or other type comprised in'a safety system for aircraft, and said fuel tank having or being provided with a special. high temperature heat and flame impermeable insulating jacket;

said high temperature heat and flame impermeable insulating jacket being especially suited and adapted to'effectiyely prevent the transfer of heat to the interior contents of tank'durlng the period of external flameor'flre, and said heat '4 and destruction of saidtank or tanks and plane. I -6. A safety tank and fuel system for aircraft, said .tank comprising and being provided with a heat and flame impermeable higlf temperature jacket preferably 'of asbestos. magnesia, or the like or equivalent,-specially andsuitably adapted to prevent the transfer, transmission or access of heat or flre to the interior of said tank orc'onten'ts during the successive-stages and progress of external flame or rim with resultant explosion insulating jacket, thereby to prevent effectively the transfer of heat to interior of tank and contents, during theco'urse -arid period of external flame or fire.

.WlLLIAM PAGET. 

